Rocket device



June l, 1948. J. o. BEAT-HE ROCKET DEVICE Filed NOV. 20, 1943 :|.E. INVENTOR i .5.a 791W w3@ Z AT Patented June 1, 1948 ROCKET DEVICE John 0. Beattie, New York, N. Y., assigner to Aerlal Products, Inc., Merrick, Long Island,

N. Y., a corporation of New York .pplication November 20, 1943, Serial No. 511,034 f7 Claims. (Cl. 102-85.6)

This inventionrelates to rocket propelled devices and more particularly to a device embodying a rocket propelled pyrotechnic candle or combustible illuminating member. The latter is adapted to be discharged from the body of the rocket device after the latter has achieved a predetermined heightv and to be suspended from a parachute as it drops to earth. The pyrotechnic candle is ignited as it is expelled from the body of the rocket casing, and in combustion which lasts for a predetermined time, emits light of great brilliancy for illuminating purposes.

A principal object of the invention is to provide a device of this character that will be effective for the purposes intended, and very simple and relatively cheap to manufacture.

A further object is to provide a device of this character that will be very simple to assemble on a mass production basis.

The rocket construction consists essentially of a rocket body assembly, and the pyrotechnic candle and parachute assembly. These subassemblies are assembled together to make a complete unit. The rocket body assembly embodies a casing providing a comparatment for propelling charge, a propelling charge in the casing, a primer for ring the charge, means to direct the products of combustion outwardly of the compartment to impart propelling and rotary motion to the rocket body in night, and a second casing adapted to receive the pyrotechnie candle and parachute assembly. The two casings are connected together to form a single body but are separated internally by suitable partitioning so that the combustion of the propulsion charge will not affect the pyrotechnic candle. The second casing also carries an expelling charge which is adapted to be fired by suitable timing or fuse means after the rocket .has been propelled to a predetermined height.

The firing of the expelling charge causes expulsion from the second casing of the pyrotechnic candle and parachute and simultaneous ignition of the pyrotechnic mix of the candle so that as the candle oats to earth its combustion emits light of great brilliancy, for example, up t 350,000 candlepower.

Since the rocket device rotates in its ilight, a likelihood of relative rotation between the pyrotechnic candle and the second casing as well as between the candle and its parachute exists. This must be avoided in order to prevent entanglement of the shrouds of the parachute with the suspension cable or cord. It is another object of the invention therefore to provide simple means for avoiding such entanglement.

To the accomplishment ofthe foregoing and such other objects as may hereinafter appear, this invention consists in the novel construction and arrangement of parts hereinafter to be described and then sought to be deflned'in the appended claims, reference being had to the accompanying drawing forming a part hereof, which shows, merely for the purposes of illustrative disclosure, a preferred embodiment .of the invention, it being expressly understood, however. that various changes may be made in practice within the scope of the 1appended claims, without digressing from the inventive idea.

In the drawing in which similar reference characters denote corresponding parts:

Fig. 1 is a longitudinal section of the device;

Fig. 2 is a transverse section taken along line 2-2 of Fig. 1;

Fig. 3 is an enlarged transverse section taken along line 3-3 of Fig. 1;

Fig. 4 is a transverse section taken along line 4-4 of Figli Fig. 5 is a bottom plan view of the device shown in Fig. 1;

Fig. 5a is a fragmentary section taken along line lia-5a of Fig. 5;

Fig. 6 is a transverse section taken along line 6-8 of Fig. 1; and

Fig. 7 is an elevational view of the pyrotechnic candle and parachute assembly as it -would appear in descent after separation from the rocket body.

Referring to the drawing, I0 denotes a rocket tube preferably of seamless or welded cold-rolled steel tubing. The tube I0 is threaded internally at II and I2 adjacent its opposite ends. It preferably is provided with a zinc plating or other protective coating or covering. The tube I0 may be of other material.

An exhaust port or end plug, or bottom member I5 preferably of cold rolled steel is threadedly engaged in the threaded portion Il of the tube I0. This plug I5 has a plurality of symmetrically spaced holes or vents I6. Each hole or vent I0 is inclined with respect to the axis of the plug. In the embodiment shown the angle of inclination is approximately 25. (See Fig. 5a.)' Other angles of inclination may be chosen. The purpose of these vents I6 will be presently described. This bottom plug I5 may be coated with zinc or other protective coating. The bottom plug I5 is bored at I1 to receive a conventional type of percussion-operated primer I8 which communicates by a vent 3 I9 with the inside of the tube I0, l may b e of other material.

A partitioning member or top plug preferably of cold rolled steel threadedly engages the threaded portion I2 of the tube I0. This top plug too may be of other material and may be zinc coated or covered with other protective coating. The plug 2|! is provided with a threaded hole 2| into which a timing ferrule or tube 22 of cold rolled steel or other material is threaded. Preferably, the hole 2| is centrally located so that the ferrule 22 extends downwardly into and concentrically about the axis of tube lll. The ferrule or tube 22 is of much smaller diameter than that of tube The plug The tube l0 contains the rocket propulsion charge which may be of any suitable type. In the embodiment shown the charge consists of a plurality of disc-like members or pellets 23 of compressed propulsion compound. These discs 23 are prepared as will be presently described and have centrally located axially extending holes 24 thereby providing a space into which the tube or ferrule 22 extends. A compression spring 25 is positioned -between the bottom plug l5 and the lowermost disc or pellet 23. This spring serves to keep the discs 23 in position. The spring may be zinc coated or otherwise covered with a protective covering. The propulsion charge may be a cylinder of single grain smokeless powder.

The ferrule 22 is open at its bottom and provided with a restricted vent 25 at its upper end. This ferrule 22 is filled with a combustible fuse or timing compound 21. Such a compound, by way of example, may consist of a compressed solidified mixture of potassium nitrate, charcoal, sulphur and calcium carbonate in proportions to be presently described. This mixture or fuse compound 21 is compressed into the tu-be or ferrule 22 and is adapted to have a predetermined burning time for a purpose to be presently described.

A carrier casing or tube 3|! is threadedly secured to the tube |0 at 3|. The casing 30 preferably is of seamless or welded cold rolled steel tubing. Other suitable material may be employed. It need not be of as thick stock as that of tube i0 and as shown in the drawing has somewhat thinner wall thickness. This casing which constitutes an extension of tube il) is adapted to carry the pyrotechnic candle, parachute and expelling charge therefor as will be described hereinafter.

A washer 32 of felt or other material is positioned in the casing adjacent to the top plug 2li. The central hole of this washer is lled with an expelling charge 33. Such charge may for example be unglazed black powder. Any other suitable composition may be used. This charge is retained in the washer by retaining discs 34, of tissue paper or other material glued or otherwise fastened to the opposite faces of said washer 32 so that the felt washer and expelling charge 33 may Ibe inserted as a unit into the casing 30.

A combustible illuminating member of pyrotechnic candle 38 is positioned in the casing 30' above the washer 32. This candle comprises a tubular casing 39 of kraft paper or other suitable material. The lower end of the casing is closed by a cap 40 of muslin or other suitable material. The candle casing 39 has a priming disc 4| of compressed priming compound to be presently described lying directly adjacent the cap 40. The latter is perforated at its center. The perforation is lled with additional priming compound 4|a applied separately to the disc 4| in any suitable manner as by painting on a wet mixture of such priming compound. Overlying the priming disc 4| is a layer 42 of starter mixture to be presently described and overlying the layer 42 is the pyrotechnic mix 43 also to be presently described which is in solidified, compressed form.

The upper end of the candle casing is closed off by a plug 45 of wood or other suitable material. This plug 45 is secured to the pyrotechnic mix as by glue and may Ibe additionally secured by screws (not shown).

A candle stop member 41 of steel or other suitable material coated with zinc or other protective coating is secured to the inner face of casing 30 as by spot welding or the like. This member 41 serves as a reinforcing abutment for the head 48a, of a nail or pin 48 that is driven through the wall of casing 39 into the wooden plug 45 to prevent rotary displacement of the candle 38 relative to the casing 30. The abutment or stop member 41 is especially necessary to take up the shock of discharge of the rocket at which time forces tending to produce relative rotation between the candle 38 and casing 30 will be of greatest magnitude. The nail or pin 48, however, is not of sufficient length or other dimensions to prevent discharge of the candle Lfrom the tube 30 when the expelling charge 33 is exploded as will be presently described.

A parachute anchor or bracket member 5U is secured to the block 45 as by screws 5| or the like. This member is substantially L-shaped and the vertical arm 52 extends into the space in case 30 above the candle 38. A parachute 54 in folded condition is positioned within the casing 30 above the candle 38. This parachute by way of example, may be a commercial baseball type, |6 shroud, 8 panel paper parachute. The suspending shrouds or cables 55 are joined together and secured to a swivel 56 which in turn is secured as by asbestos cord 51 at 58 to the parachute anchor 50.

A washer 60 of felt or other desirable material is provided in the casing 30 below the parachute 54. This washer is designed to protect the parachute 54 from the products of combustion of the expelling charge 33.

The suspending cables 55 are packed about the anchor arm 52 without encircling it. A second washer 60a of felt or the like overlies the packed shroud 55. A disc 6| of wax paper or other suitable material overlies the washer 60a and prevents absorption by the latter of any compound with which the parachute may have' been heated. A sleeve 62 of paper or the like surrounds the parachute 54. This sleeve facilitates packing and prevents contact between the parachute and the container 30. The parachute 54 is packed in conventional manner and positioned in the sleeve 62 about the anchor arm 52 so that rotation of candle 38 will necessarily rotate the parachute and thereby prevent any entanglement of the shrouds 55 and anchor arm 52.

A nose cap 64' of drawn sheet steel or other suitable material is provided to close the upper end of casing 30. The cap 64 is coated with zinc or other protective coating. It has convex shape to provide a bluntly-pointed nose for the assembled device and is adapted to be retained on the casing 30 frictionally so that it will be pushed or blown off when the expelling charge 33 is fired.

In the embodiment shown, a cup-like member 65 is secured to the inner face of the nose 64 as by spot-welding or the like. I'his cup-like member 65 of the same material as member 54 extends outwardly ofthe latter at 66. The portion 33 has a diameter admeasured to frictionally engage within the upper end of casing 30. The top 51 of the member 65 acts to prevent the parachute 54 from being driven into the pointed portion of the nose cap 84k.

In operation. the projectile described is adapted to be ilred from a mortar having a firing pin. When the projectile is dropped onto the firing pin in the mortar, the pin strikes the primer I8 exploding the latter. This explosion ignites the propelling compound or propulsion charge 23 and at the same time ignites the timing charge or fuse 21 in the ferrule 22. The products of combustion of the propelling compound 23 vent through the vents or orifices I6 in the base plug IE, driving the projectile from the mortar and to a high elevation. The angular disposition of the vents I6 causes the projectile to whirl about its longitudinal axis during flight. When the projectile achieves a predetermined height between 1400 to 1600 feet in the embodiment shown, the timing or fuse compound 21 has burned out so as to ignite the expelling charge 33. The latter explodes and drives the candle 38 and parachute 54 outwardly of the forward end of casing 30 blowing or pushing olf the nose cap 64 in such action. The top 61 of member 65 prevents the parachute from being blown into the member 64. At the same time, the explosion of the expelling charge 33 fires the priming pellet 4| of the pyrotechnic candle 38, which in turn ignites the starter mixture 42 thereof and, in turn, causes silicon and potassium nitrate both in finely di- Parts Potassium nitrate 12 Willow charcoal..."` 8 Sulphur 2 Dextrin 11/2 The homogeneous mixture is dampened with water and pressed in a mold under a static load of ,1000 lbs. into the solid disc 4|. The priming composition 4'| a is of the same material but simply painted onto the disc 4|. The proportions are by weight.

The starter mixture 42 may comprise a homogeneous mixture of equal parts by weight of fused vided form.

The pyrotechnic mix 43 comprises a homogeneous mixture in finely divided form of The magnesium is coated with the linseed oil at least 48 hours before its incorporation with i the remainder of the pyrotechnic mix. This is the pyrotechnic mix 43 to burn from the bottom up as the candle 38 falls. The fall of the candle is retarded by the parachute 54 from which it is suspended and which then opens so that the burning candle 38 falls slowly to earth. The pyrotechnic mix 43 is of such composition that it burns for a minimum time of about Lminute with a brilliancy of at least 350,000 candle power. The discs or pellets 23 of the propulsion charge may be composed of the following materials:

. Per cent Potassium nitrate '75 Charcoal 15 Sulphur 10 in ilnely divided form constituting a meal. This meal is mixed with calcium carbonate in the following proportions: meal 16 parts, calcium carbonate 2 to 6 parts. This mixture is mixed thoroughly and molded under pressure in molds to produce the discs or pellets 23.

The proportion of parts and percentages is by weight.'

The timing or fuse compound 21 may consist of a mixture of 16 parts by weight of the above described meal and 31/2 parts by weight of calcium carbonate. This mixture after thorough rumbling to insure homogeneity of mix is incorporated into the ferrule by pressing successive increments of the mix into the ferrule under static loads' of 2000 lbs. In the embodiment shown, eight successive increments each increment loaded under the same conditions have Y been incorporated into the ferrule 22. The burning time of the timing compound can be anything desired depending upon the length of the ferrule. In the embodiment shown, the burning time is approximately seven seconds plus or mnus one second.

'The priming disc or pellet 4| of the pyrotechnic candle may consist of a homogeneous mixture of nely divided very important. The lithographic varnish is homogeneously mixed with the barium nitrate.

The linseed oil-coated magnesium and barium nitrate-lithographic varnish mixture is then combined with the grain aluminum and calcium oxalate and mixed thoroughly.

This pyrotechnic mixture is then utilized to prepare the candle 38 as follows: The candle case 39 is placed into a mold. The priming pellet 4| is placed at the bottom of the case. Then a small quantity (about 1 gram in this instance) of the starter mixture 42 is poured over the pellet 4| Then a first increment of the pyrotechnic mix 43 is placed in the candle case. and pressed under a static load of 20,000 lbs. Nine more successive increments of pyrotechnic mix each compressed under a static load of 20,000 lbs. are pressed into the case. Then hot glue is spread over the top increment and the wood plug'45 attached. Then the muslin disc 40 is glued over the bottom of the candle case 39, care being taken to avoid glueing its central portion to the disc 4|. The 'unglued portion of the muslin cap 40 is then cut out and the priming mix 4| a painted on disc 4| to ll the opening left by the cut out portion of cap 40. The solid candle 38 is thus produced for insertion as a unit into the casing 30.

While specific examples of propulsion, timing, priming, starting, and pyrotechnic compounds have been described herein, it is to be understood that these are by way of example only. There is no intention of limitation to the speclc ingredients or proportions mentioned as these will vary to meet diierent operating conditions.

It Should be expressly understood that propellants other than black powder can be used. For

- example, a smokeless powder cylinder can re- 7 in the casing I in place of the primer I8 and ignited when current is applied.

In the assembly, all threaded joints are sealed in usual manner by the use of white lead or the like (not shown). This is especially important in connection with the threaded joints between the partitioning member 32 and the tubes I0 and 22 so as to prevent leakage of the combustion gases of the propulsion charge 23 into the candle casing 30, If such leakage occurred, premature explosion of the expelling charge 33 and ignition of candle 38 would take place. The partitioning member 32 is of sufficient strength to resist any tendency of the combustion of the propulsion charge 23 to drive it forwardly.

The material of the various parts while speciecl particularly may be changed to meet differ-V ent operating conditions.

While specific structural details have been shown and described, it is to be understood that variation in structure and of materials within the scope of the appended claims is contemplated. There is no intention of limitation to the exact details shown and described.

What is claimed is:

1. In a device of the character described, a tubular casing, rocket propulsion charge in said casing, means for firing said charge, an end plate having biased orifices for venting the products of combustion of said charge rearwardly of said casing and for imparting rotary motion to the ight of the device, a seco-nd casing secured to said rst-named casing and providing a continuation thereof, a pyrotechnic candle in said secondnamed casing, means for separating said pro pulsion charge from said pyrotechnic candle, an expulsion charge in said second casing, means for igniting said expulsion charge at a predetermined time lafter said propulsion charge has been red to expel said candle from said second casing, an lanchoring member secured to said candle and having a portion extending forwardlyvthereof, a parachute positioned about said forwardly extending portion, suspending means connecting said parachute to said forwardly extending portion, an abutment carried by said second casing, and means extending from a Iportion of said candie for engagement with said abutment for preventing relative rotation of said candle with respect to said casing during flight of said device to prevent entanglement of the suspending means with shrouds of said parachute.

2. A rocket-propelled illuminating device comprising a casing having a compartment for rocket propulsion charge, and a second compartment, a plurality of discs of compressed rocket propulsion charge in said first-named compartment, a compression spring -for maintaining the discs in position, an end member at the trailing end of said casing having angularly disposed passageways for discharging the products of combustion of said charge rearwardly and angularly to impart whirling motion to the device 'in night, said spring lying between the said end member and the lowermost of said discs in said first-named compartment, percussion means for ring said charge carried by said end member, combustible illuminating means in solid form in said "second compartment, a parachute therein attachedto said combustible illuminating means, an expelling charge in said second compartment for discharging its contents forwardly of said casing and adapted in such expulsion to ignite said illuminatingmeans, and time fuse means extending into said first-named compartment and adapted 8 to be ignited by the iiring of said propulsion charge and to re said expelling charge a predetermined time thereafter.

3. A rocket-propelled illuminating device comprising a multi-sectioned casing whose sections are separable, a compartment in one of said sections for rocket propulsion charge, a plurality of discs of propulsion charge in said compartment, a compression spring for maintaining said discs in position, a closure member at the trailing end of said compartment having angularly disposed passageways for discharging the products of combustion of said discs rearwardly and angularly to impart forward and whirling motion to the device in iiight, said spring lying between the lowermost of said discs and said closure member, percussion means carried by said closure member for igniting said discs, a second compartment in another of said separable sections, a partitioning member completely separating said two compartments, an expelling charge in said second compartment adjacent to said partitioning member, time fuse means extending from said partitioning member into said rst compartment and communicating with said second compartment, said time fuse means being adapted to be ignited by the combustion of said discs and to ignite said expelling charge a predetermined time after the ignition of said discs, acombustible illuminating member carried in said second compartment adjacent to said expelling charge, an anchoring member secured to said illuminating member, a parachute positioned about said anchoring member, coupling means for joining said anchoring member and said parachute, and a removable closure member for the leading end of said device, said illuminating member being ignited by the ilring of said expelling charge and being expelled from said second compartment together with said parachute by the explosion of said expelling charge.

4. A rocket-propelled illuminating device comprising a casing, rocket propulsion charge in separate units of solidified form in said casing, means for firing said charge, a combustible illu minating member in said casing, means in said casing for maintaining said charge and said member separate and for preventing access to said member of the products of combustion of said charge, means for directing said products of combustion rearwardly and angularly relative to the axis of said device to propel it forwardly with a whirling motion, means for firing said charge, means for expelling said member from said casing a predetermined time after the firing of said charge, said combustible member being in solid form, a substantially L-shaped anchoring member one of whose arms is secured to an end of said combustible illuminating member and the other of whose arms extends forwardly of said end of said combustible illuminating member, a parachute positioned about said other of said arms. means joining said parachute to said other of said arms of said anchoring member, an abutment on said casing and means extending from a portion of said illuminating member for engagement with said abutment to prevent relative rotation between said casing and said combustible member during flight of the device and to avoid entanglement of said joining means with said anchoring means on expulsion of said combustible member and said parachute from said casing.

5. A rocket-propelled illuminating device comprising a casing having a compartment for rocket propulsion charge, and a second compartment.

rocket propulsion charge in said first-named compartment, a compression spring for maintaining the charge in position, an end member at the trailing end of said casing having angularly disposed passageways for discharging the products of combustion of said charge rearwardly and angularly to impart whirling motion to the device in flight, said spring lying between the said end member and the lowermost end of said charge in said first-named compartment carried by said end member, combustible illuminating means in solid form in said second compartment, a parachute therein attached to said combustible illuminating means, an expelling charge in said second compartment for discharging its contents forwardly of said casing and adapted in such expulsion to ignite said illuminating means, and time fuse means extending into said rst-named compartment and adapted to be ignited by the firing of said propulsion charge and to fire said expelling charge a predetermined time thereafter.

6. A rocket-propelled illuminating device comprising a multi-sectioned casing whose sections are separable, a compartment in one of said sections for rocket propulsion charge, propulsion charge in said compartment, a compression spring for maintaining said charge in position, a closure member at the trailing end of said compartment having angularly disposed passageways for discharging the products of combustion of said charge rearwardly and angularly to impart forward and whirling motion to the device in flight, said spring lying between the lowermost end of said charge and said closure member, percussion means carried by said closure member for igniting said charge, a second compartment in another of said separable sections, a partitioning member completely separating said two compartments, an expelling charge in said second compartment adjacent to said partitioning member, time fuse means extending from said partitioning member into said first compartment and communicating with said second compartment, said time fuse means being adapted to be ignited by the combustion of said propulsion charge and to ignite said expelling charge a predetermined time after the ignition of said propulsion charge. a combustible illuminating member carried in said second compartment adjacent to said expelling charge. an anchoring member secured to said illuminating member, a parachute positioned about said anchoring member, coupling means for Joining said anchoring member and said parachute, and a removable closure member for the leading end of said device, said illuminating member being ignited by the firing of said expelling charge and being expelled from said second compartment together with said parachute by the explosion of said expelling charge.

7. A rocket-propelled illuminating device comprising a casing, rocket propulsion charge in solidified form in said casing, means for firing said charge, a combustible illuminating member in said casing, means in said casing for maintaining said charge and said member separate and for preventing access to said member of the products of combustion of said charge, means for directing said products of combustion rearwardly and angularly relative to the axis of said device to propel it forwardly with a whirling motion, means for firing said charge, means for expelling said member from said casing a predetermined time after the firing of said charge, saidv combustible member being in solid form, a. substantially L-shaped anchoring member one of whose arms is secured to an end of said combustible illuminating member and the other of whose arms extends forwardly of said end of said combustible illuminating member, a parachute positioned about said other of said arms, means joining said parachute to said other of said arms of said anchoring member, an abutment on said casing and means extending from a portion of said illuminating member for engagement with said abutment to prevent relative rotation between said casing and said combustible member during flight of the device and to avoid entanglement of said joining means with said anchoring means on expulsion of said combustible vmember and said parachute from l Number said casing.

JOHN O. BEATTIE.

REFERENCES CITED The following references are of record in the ille of this patent:

UNITED STATES PATENTS FOREIGN PATENTS Country Date Great Britain Apr. 15, 1920 Great Britain Nov. 5, 1928 France Feb. 26, 1920 Number 

